CN106793651B - Direct-insertion type box structure of control board at top of aircraft cockpit - Google Patents
Direct-insertion type box structure of control board at top of aircraft cockpit Download PDFInfo
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- CN106793651B CN106793651B CN201611132195.0A CN201611132195A CN106793651B CN 106793651 B CN106793651 B CN 106793651B CN 201611132195 A CN201611132195 A CN 201611132195A CN 106793651 B CN106793651 B CN 106793651B
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- 230000007246 mechanism Effects 0.000 claims description 6
- 239000003292 glue Substances 0.000 claims description 4
- 230000013011 mating Effects 0.000 claims description 3
- 230000037431 insertion Effects 0.000 abstract description 8
- 238000009434 installation Methods 0.000 description 10
- QMUDLTGWHILKHH-UHFFFAOYSA-N 1,2,5-trichloro-3-(3,5-dichlorophenyl)benzene Chemical compound ClC1=CC(Cl)=CC(C=2C(=C(Cl)C=C(Cl)C=2)Cl)=C1 QMUDLTGWHILKHH-UHFFFAOYSA-N 0.000 description 5
- 238000012423 maintenance Methods 0.000 description 5
- 239000002184 metal Substances 0.000 description 5
- 238000010276 construction Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 238000000605 extraction Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009833 condensation Methods 0.000 description 1
- 230000005494 condensation Effects 0.000 description 1
- 238000002788 crimping Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/02—Arrangements of circuit components or wiring on supporting structure
- H05K7/10—Plug-in assemblages of components, e.g. IC sockets
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R12/00—Structural associations of a plurality of mutually-insulated electrical connecting elements, specially adapted for printed circuits, e.g. printed circuit boards [PCB], flat or ribbon cables, or like generally planar structures, e.g. terminal strips, terminal blocks; Coupling devices specially adapted for printed circuits, flat or ribbon cables, or like generally planar structures; Terminals specially adapted for contact with, or insertion into, printed circuits, flat or ribbon cables, or like generally planar structures
- H01R12/70—Coupling devices
- H01R12/71—Coupling devices for rigid printing circuits or like structures
- H01R12/72—Coupling devices for rigid printing circuits or like structures coupling with the edge of the rigid printed circuits or like structures
- H01R12/73—Coupling devices for rigid printing circuits or like structures coupling with the edge of the rigid printed circuits or like structures connecting to other rigid printed circuits or like structures
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- Engineering & Computer Science (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Connection Or Junction Boxes (AREA)
- Details Of Connecting Devices For Male And Female Coupling (AREA)
Abstract
The invention provides an aircraft cockpit top control panel direct-insertion type box structure, which comprises a control panel assembly, a bus plate assembly, a large box body and a guide structure, wherein the control panel assembly is arranged on the top of the aircraft cockpit; the busbar assembly is mounted on the large box, and the control panel assembly comprises at least one control panel, and the control panel is connected with the busbar assembly through the guide structure and the board-to-board connector. The control panels are not provided with electric modules respectively, and no independent electromagnetic shielding rear cover is arranged, and the electric modules are arranged on the bus plate to form a bus plate assembly. Each control panel establishes an electrical connection with a board-to-board connector receptacle on the bus bar board through a board-to-board connector plug. Each control panel realizes blind insertion of the board-to-board connector through the guide structure, and is fixed on the large box body through the quick-release fastener. The small wire harnesses on the intermediate connector matched with the back connector of the bus plate are summarized into a larger wire harness, the larger wire harnesses are concentrated on the circular connector on the large box body, and connection is established with the outside through the circular connector.
Description
Technical Field
The invention relates to a box structure, in particular to a direct-insertion box structure of a control board at the top of an aircraft cockpit.
Background
Currently, the domestic aircraft cockpit roof panel products (see fig. 1) take the form of a structural frame 2 'and a control panel assembly (comprising a plurality of control panels 11') each having an electrical and mechanical interface with the aircraft. The top control board control panel assembly is arranged on the frame structure 2', and is electrically connected with each other by adopting a cable 3'. Such a frame structure and control panel assembly have the following disadvantages:
(1) The manufacturing is complex: each control panel has an electromagnetic shielding rear cover 114', a circular connector 115', a metal base plate 117', an electrical module 118', etc. (see fig. 2), and it can be seen that many parts are required to be installed, and the manufacturing cost and the weight are high;
(2) The maintenance is inconvenient: when in maintenance, besides the mechanical fixing piece of the control panel is detached (fastened), the cable 3' plug of the control panel is required to be pulled out or plugged in, and the detachment is time-consuming;
(3) The difficulty of cable laying is high: when the control panel assembly is installed on the frame structure 2', internal wiring of the top control board is carried out according to the electrical interface of each control panel, and the cable laying is time-consuming and labor-consuming under the influence of the operating environment and the installation space;
(4) Each control panel needs to be electromagnetically shielded: each control panel is provided with an electromagnetic shielding rear cover;
(5) Each control panel needs to be subjected to heat dissipation design: the high power consumption electric module on each control panel is tightly adhered to the metal bottom plate 117' by heat conducting glue or heat conducting pad, so that the heat resistance is reduced as much as possible, and the heat is led out along the shell;
(6) Greater cable length: in order to ensure that each control panel is detachable, a cable with enough length is reserved at the rear part of the control panel, and the weight of the product is increased.
Disclosure of Invention
The invention aims to provide an in-line box structure of a control board at the top of an aircraft cockpit, so as to overcome the defects of the prior design of the control board in practical application.
In order to achieve the above purpose, the technical scheme of the invention is as follows:
An aircraft cockpit top control panel direct insertion type box structure comprises a control panel assembly, a bus bar assembly, a large box body and a guide structure; the busbar assembly is mounted on the large box, and the control panel assembly comprises at least one control panel, and the control panel is connected with the busbar assembly through the guide structure and the board-to-board connector.
Further, the big box includes frame construction and back shroud, frame construction includes curb plate, transverse rib board and vertical ribbed slab all around, be equipped with on the vertical ribbed slab and walk silk rail and backing sheet, be equipped with installation tab and circular connector on the outer wall of curb plate all around, be equipped with the mounting hole on the installation tab.
Further, the guiding structure comprises a first stage guiding structure and a second stage guiding structure; the first-stage guide structure comprises a guide pin assembly arranged on the control panel and a guide sleeve assembly arranged on the busbar board assembly, wherein the guide pin assembly comprises a guide pin, a spring base and an elastic retainer ring, and the guide sleeve assembly comprises a guide sleeve, a flat pad, an elastic pad and a nut, wherein a jack matched with the guide pin is arranged in the guide sleeve; the second-stage guide structure comprises a board-to-board connector plug arranged on the control panel and a board-to-board connector socket arranged on the bus bar assembly, wherein the board-to-board connector plug comprises a plug guide pin and a plug guide sleeve, and the board-to-board connector socket comprises a socket guide sleeve and a socket guide pin which correspond to the plug guide pin and the plug guide sleeve respectively.
Further, the distance from the end face of the plug guide pin to the control panel PCB is larger than the distance from the end face of the plug guide sleeve to the control panel PCB; the distance from the end face of the socket guide pin to the bus plate is larger than the distance from the end face of the socket guide sleeve to the bus plate; the distance from the end face of the plug guide pin to the control panel PCB is equal to the distance from the end face of the socket guide pin to the bus bar; the distance from the end face of the plug guide sleeve to the control panel PCB is equal to the distance from the end face of the socket guide sleeve to the bus bar.
Further, the distance from the end face of the guide pin to the control panel PCB is larger than the distance from the end faces of the plug guide pin and the plug guide sleeve to the control panel respectively; the distance from the end face of the guide sleeve to the bus plate is smaller than the distance from the socket guide pin and the end face of the socket guide sleeve to the bus plate respectively.
Further, the bus plate assembly comprises a bus plate, wherein the front surface of the bus plate is provided with a plate-to-plate type connector socket, an electric module of an external shielding box and a guide sleeve assembly, and the back surface of the bus plate is provided with an intermediate connector connected with the circular connector and an electric module of the external shielding box; the electric module is tightly attached to the shielding box through heat conducting glue.
Further, the control panel comprises a PCB board, and a board-to-board connector plug and a guide pin assembly are arranged on the PCB board.
Further, the in-line box structure of the aircraft cockpit top control plate also comprises a spring mechanism (comprising a spring, a spring base and a circlip) in which a screw assembly is used for replacing the guide pin assembly. The screw assembly comprises a pull-out screw, a fixed washer and a mounting base, and is convenient to take the control panel off the large box body.
Further, the small wire harness on the middle connector on the back of the bus bar assembly is assembled into a large wire harness and is concentrated on the circular connector on the large box body, and connection is established with the outside through the circular connector.
The technical scheme of the invention also comprises the following steps:
an installation method of an in-line box structure of a top control panel of an aircraft cockpit, comprising the following steps:
step 1: connecting one end of a wire harness to the intermediate connector and the other end thereof to the circular connector, and fixing the wire harness to the frame structure;
step 2: installing a bus plate provided with a guide sleeve and a board-to-board type connector socket on a frame structure;
Step 3: installing the intermediate connector on a busbar assembly;
step 4: fixing a back cover plate on the frame structure;
step 5: installing a guide pin and a board-to-board type connector plug on a control panel PCB, wherein the control panel realizes accurate opposite insertion through a guide structure;
Step 6: the control panel is fixed on the wire track of the large box body through a quick-release fastener.
Compared with the prior art, the technical scheme of the invention has the following beneficial effects:
(1) The manufacturing parts are few: each control panel eliminates an electric module, an electromagnetic shielding rear cover, a round connector, a metal bottom plate and the like, and the parts required for installation are greatly reduced;
(2) The maintenance is convenient: during maintenance, the control panels can be taken down for maintenance only by loosening and detaching the quick-release fasteners;
(3) The fixed cable is directly inserted without excessive length, so that the number of cables is reduced, and the weight is reduced;
(4) The two-stage guiding realizes the accurate opposite insertion of the connector, and further, the blind insertion of the connector is realized;
(5) Has the advantages of integral waterproof and dustproof protection, integral electromagnetic shielding design (an electric module with a shielding box) and concentrated heat dissipation design.
Drawings
FIG. 1 is a schematic view of a prior art aircraft cockpit top control panel product;
FIG. 2 is a schematic diagram of a control panel according to the prior art;
FIG. 3 is a schematic view of an installation of one embodiment of an aircraft cockpit top control panel in-line box structure according to the present invention;
FIG. 4 is a schematic view of one embodiment of an in-line box structure for an aircraft cockpit top control panel according to the present invention;
FIG. 5 is a schematic illustration of a specific construction of one embodiment of an aircraft cockpit top control panel in-line box structure according to the present invention;
FIG. 6 is a schematic view of a portion of a control panel of one embodiment of an in-line box structure for an aircraft cockpit top control panel according to the present invention;
FIG. 7 is a schematic view of the guiding structure in one embodiment of the aircraft cockpit top control panel in-line box structure of the present invention;
fig. 8 is a schematic diagram illustrating the functional structure of a screw assembly in one embodiment of an in-line box structure for an aircraft cockpit roof control panel according to the present invention.
Reference numerals:
1-control panel assembly, 11-control panel, 111-PCB board, 112-support structure, 113-panel, 2-busbar board assembly, 21-busbar board, 22-electrical module, 23-electrical module, 3-large box, 31-frame structure, 32-back cover, 311-wire track, 312-support tab, 313-mounting tab, 314-round connector, 315-mounting hole, 4-guide structure, 41-guide pin assembly, 411-guide pin, 412-spring, 413-spring mount, 414-circlip, 42-guide sleeve assembly, 421-guide sleeve, 422-flat pad, 423-spring pad, 424-nut, 5-board-to-board connector plug, 51-plug guide pin, 52-plug guide sleeve, 6-board-to-board connector socket, 61-socket guide pin, 62-socket guide sleeve, 7-busbar board back connector, 9-screw assembly, 91-extraction screw, 92-fixing washer, 93-mounting mount;
11' -control panel, 2' -structural frame, 3' -cable, 114' -electromagnetic shield back cover, 115' -circular connector, 117' -metal chassis, 118' -electrical module.
Detailed Description
Referring to fig. 3-8, wherein fig. 3 is a schematic view illustrating the installation of one embodiment of an in-line box structure for an aircraft cockpit top control panel according to the present invention; FIG. 4 is a schematic view of one embodiment of an in-line box structure for an aircraft cockpit top control panel according to the present invention; FIG. 5 is a schematic illustration of a specific construction of one embodiment of an aircraft cockpit top control panel in-line box structure according to the present invention; FIG. 6 is a schematic view of a portion of a control panel of one embodiment of an in-line box structure for an aircraft cockpit top control panel according to the present invention; FIG. 7 is a schematic view of the guiding structure in one embodiment of the aircraft cockpit top control panel in-line box structure of the present invention; fig. 8 is a schematic diagram illustrating the functional structure of a screw assembly in one embodiment of an in-line box structure for an aircraft cockpit roof control panel according to the present invention.
In one embodiment, a top control panel in-line box structure capable of being located in an aircraft cockpit includes a control panel assembly 1, a busbar assembly 2, a large box 3, a guide structure 4, each of which is not separately equipped with an electrical module, and no separate electromagnetic shield back cover. The electrical modules 22 and 23, the board-to-board connector receptacle 6 and the busbar rear connector 7 are mounted on the busbar 21 to form the busbar assembly 2. The busbar assembly 2 is mounted on a large box 3. Each control panel establishes an electrical connection with a board-to-board connector receptacle 6 on the bus bar board by means of a board-to-board connector plug 5. Each control panel realizes blind insertion of the board-to-board connector through the guide structure 4, and is fixed on the large box body 3 through the quick-release fastener. The small wire harnesses on the intermediate connector (not shown) mating with the intermediate connector 7 on the back of the busbar board 21 are collected into a larger wire harness and concentrated on several circular connectors 314 on the large box 3, and a connection is established with the outside through the circular connectors 314.
In the embodiment, the PCB 111 on the control panel is pushed into and fixed by the clamping column; by individually shielding the electrical modules 22 and 23 on the bus bar plate 21; the large box body 3 is provided with an integrated metal sheet rear cover plate 32, so that the technical problems caused by impact, vibration, (condensation on a ceiling structure) dripping water and the like are solved; the high-power consumption electric modules are intensively arranged on the bus plate 21 and are tightly attached to the shielding box by using heat-conducting glue; the board-to-board connector has a tape guide and error protection structure; the board-to-board connector has a certain amount of plugging force so as to ensure reliable connection in the environments of impact, vibration and the like; the bus bar plate 21 is floatingly mounted on the large case 3; the guide structure 4 is internally provided with a spring mechanism to overcome the pull-out force of the board-to-board connector, so that the control panel is convenient to take down.
In one embodiment, a method of installing the aircraft cockpit top control panel in-line box structure includes the steps of: the frame structure 31 is installed: the frame structure 31 has peripheral side plates, cross ribs, vertical ribs, lugs 313 and wire tracks 311 mounted thereon; crimping (or welding) the wire harness to a mounting point corresponding to an intermediate connector that mates with the back connector 7 of the bus bar 21; the other end of the wire harness is crimped to a circular connector 314 on the frame structure 31; the guide sleeve assembly 42 is secured through mounting holes in the busbar plate 21. Fixing the wire harness to the frame structure 31, and plugging the intermediate connector to the back surface of the bus bar plate 21; mounting the bus bar 21 on the frame structure 31; fixing the back cover plate 32 to the frame structure 31; a guide pin assembly 41 (guide pin, spring mechanism, etc.) is mounted on each control panel; each control panel realizes the accurate opposite insertion of the board-to-board connector through the guide structure 4; each control panel is fixed on the wire track of the large box body 3 through a quick-release fastener.
In another installation embodiment, the invention relates to a detachable structure form of the in-line box structure of the control panel at the top of the cockpit of the aircraft, which comprises the following contents: the spring mechanism in the guide structure is eliminated, and the quick release pull screw assembly 9 (see fig. 8) is mounted on the control panel. The extraction screw assembly includes an extraction screw 91, a securement washer 92, and a mounting base 93. When the control panel is taken out, the quick release pull screw 91 is loosened to make the screw head spring up, and the control panel is taken down by grasping the pull screw 91 by hand (at this time, the quick release fastener on the control panel is loosened). When the control panel is installed, the quick release pull screw 91 is tightened to sink into the panel 113.
In another embodiment, the electrical module of the add-on shield can is mounted on a large housing.
Figures 3, 4 and 5 show block diagrams of the in-line box of the aircraft cockpit top control panel of the present invention, including: control panel assembly 1, busbar board assembly 2, big box 3, guide structure 4. A control panel assembly 1 comprising a plurality of control panels (only control panel 11 is illustrated in fig. 5); a busbar assembly 2 having a board-to-board connector receptacle 6 and an electrical module 22 of an add-on shield box on its front face and having a connector 7 and an electrical module 23 of an add-on shield box on its back face mating with an intermediate connector of a round connector on a large box. The bus bar plate 21 is fixed by the support piece 312 on the vertical rib of the large case 3, while the guide bush assembly 42 is fixed through the mounting hole on the bus bar plate 21 and through the through hole on the support piece 312. The large case 3 is composed of a frame structure 31 and a back cover plate 32. The frame structure 31 has wire rails 311 on the vertical ribs of the mounting frame structure 31, mounting tabs 313 on the side panels around the mounting frame, the mounting tabs having mounting holes 315, and circular connectors 314. The guide structure 4 includes a first guide structure including a guide pin assembly 41 (see fig. 6) and a guide sleeve assembly 42, and a second guide structure.
Fig. 6 is a structural view of a control panel of the present invention having a panel 113, a board-to-board connector plug 5 soldered to a PCB board 111, and a guide pin assembly 41 secured to a support structure 112 thereof.
Fig. 7 is a two-stage guide structure of the present invention, the two-stage guide connector structure comprising:
The first stage of the guide structure includes a guide pin assembly 41 (see fig. 6) on the control panel, and a guide sleeve assembly 42 (see fig. 5) on the bus bar. The guide pin assembly 41 includes: a guide pin 411, a spring 412, a spring mount 413 and a circlip 414; the guide sleeve assembly 42 includes: a guide sleeve 421, a flat pad 422, a spring pad 423 and a nut 424;
The second stage of guiding comprises guiding pins and guiding sleeves on the board-to-board connector plug 5 and the board-to-board connector socket 6.
In one embodiment, a jack matched with the guide pin 411 is formed in the guide sleeve 421; the spigot end of the guide pin 411 has a tapered structure, and correspondingly, the spigot end of the guide sleeve 421 has an involute structure, so that the guide pin 411 slides into the guide sleeve 421. Further, a slot is formed at the end of the guide pin 411 to facilitate the installation of the guide pin 411; the outer shape of the guide sleeve 421 is hexagonal, so as to facilitate the installation of the guide sleeve 421. Further, the guide sleeve 421 is provided with a hole for letting out the circlip 414, so that the guide sleeve 421 has a contact stroke with the spring base 413.
In one embodiment, the board-to-board connector plug 5 includes a plug guide pin 51 and a plug guide sleeve 52, having an error-proof function. And the end face of the plug guide pin 51 is higher than the end face of the plug guide sleeve 52. The board-to-board connector receptacle 6 includes a receptacle guide pin 61 and a receptacle guide sleeve 62, and has an error-proof function. The end face of the socket guide pin 61 is higher than the end face of the socket guide sleeve 62, the socket guide pin 61 is equal to the plug guide pin 51 in height, and the socket guide sleeve 62 is equal to the plug guide sleeve 52 in height, so that the balance and the stress are kept when the board-to-board connector plug 5 and the board-to-board connector socket 6 are inserted in opposite directions.
Further, the distance from the end face of the guide pin 411 to the control board PCB 111 is larger than the distance from the end face of the plug guide pin 51 to the control board PCB 111, and also larger than the distance from the end face of the plug guide sleeve 52 to the control board PCB 111. The distance from the end surface of the guide sleeve 421 to the bus bar 21 is slightly smaller than the distance from the end surface of the socket guide sleeve 62 to the bus bar 21, and is also smaller than the distance from the end surface of the socket guide pin 61 to the bus bar 21. When the board-to-board connector plug 5 is inserted into the board-to-board connector receptacle 6, the contact between the guide pins 411 and the guide sleeves 421 is prior to the contact between the plug guide pins 51 and the receptacle guide sleeves 62, and the contact between the plug guide sleeves 52 and the receptacle guide pins 61. When the board-to-board connector plug 5 is separated from the board-to-board connector receptacle 6, the plug guide pins 51 are separated from the receptacle guide bush 62 and the plug guide bush 52 are separated from the receptacle guide pin 61 before the guide pins 411 are separated from the guide bush 421. Ensuring that the first-stage rough guide of the guide pin 411 and the guide sleeve 421 is firstly carried out, then the second-stage accurate guide of the plug guide pin 51 and the socket guide sleeve 62 as well as the plug guide sleeve 52 and the socket guide pin 61 is carried out, ensuring that the contact bodies on the connectors 5 and 6 are not damaged in the process of opposite insertion and separation of the board-to-board connector plug 5 and the board-to-board connector socket 6, and ensuring the connection reliability of the connectors.
In one embodiment, the guide pins 411 on the control panel 11 slide into the blind holes of the guide sleeve 421; the quick-release fastener on the control panel enters the corresponding mounting hole on the wire track 311; applying external force to the control panel to enable the control panel to be close to the wire track 311; under the action of the external force, the guide sleeve 421 is in contact with the spring base 413 and applies pressure thereto; the spring base 413 transmits pressure to the spring 412, which is compressed, so that the distance between the PCB 111 and the bus bar 21 is gradually reduced; the plug guide pin 51 contacts the socket guide sleeve 62, and the plug guide sleeve 52 contacts the socket guide pin 61; the connectors 5 and 6 are inserted in place; the quick release fasteners on the control panel are locked to secure the control panel to the wire track 311. And releasing the quick release fastener on the control panel. Under the action of restoring force, the spring base 413 and the guide sleeve 421 are downwards moved by the spring to separate the connectors 5 and 6; the plug guide pins 51 are separated from the receptacle guide sleeves 62, and the plug guide sleeves 52 are separated from the receptacle guide pins 61. The guide sleeve 421 is separated from the spring mount 413. The control panel is removed from the track 311.
A plurality of control panels are installed on the wire rails 311 in the case 3 of fig. 4 and 5 by means of quick connection, wherein the plurality of control panels are installed in the case 3 such that the top control panels are an integrated integral structure.
The above description of the specific embodiments of the present invention has been given by way of example only, and the present invention is not limited to the above described specific embodiments. Any equivalent modifications and substitutions for the present invention will occur to those skilled in the art, and are also within the scope of the present invention. Accordingly, equivalent changes and modifications are intended to be included within the scope of the present invention without departing from the spirit and scope thereof.
Claims (6)
1. The direct-inserting type box body structure of the control board at the top of the aircraft cockpit is characterized by comprising a control panel assembly, a bus bar assembly, a large box body and a guide structure; the bus plate assembly is arranged on the large box body, the control panel assembly comprises at least one control panel, and the control panel is connected with the bus plate assembly through the guide structure and the plate-to-plate connector; the large box body comprises a frame structure and a rear cover plate, wherein the frame structure comprises four side plates, a transverse rib plate and a vertical rib plate, a wire running rail and a supporting sheet are arranged on the vertical rib plate, mounting lugs and a circular connector are arranged on the outer wall of the four side plates, and mounting holes are formed in the mounting lugs; the guide structure comprises a first-stage guide structure and a second-stage guide structure; the first-stage guide structure comprises a guide pin assembly arranged on the control panel and a guide sleeve assembly arranged on the busbar board assembly, wherein the guide pin assembly comprises a guide pin, a spring base and an elastic retainer ring, and the guide sleeve assembly comprises a guide sleeve, a flat pad, an elastic pad and a nut, wherein a jack matched with the guide pin is arranged in the guide sleeve; the second-stage guide structure comprises a board-to-board connector plug arranged on the control panel and a board-to-board connector socket arranged on the bus bar assembly, wherein the board-to-board connector plug comprises a plug guide pin and a plug guide sleeve, and the board-to-board connector socket comprises a socket guide pin and a socket guide sleeve which correspond to the plug guide pin and the plug guide sleeve respectively.
2. The aircraft cockpit top control panel in-line box structure of claim 1 wherein the distance from the end face of the plug guide pin to the control panel PCB is greater than the distance from the end face of the plug guide sleeve to the control panel PCB; the distance from the end face of the socket guide pin to the bus plate is larger than the distance from the end face of the socket guide sleeve to the bus plate; the distance from the end face of the plug guide pin to the control panel PCB is equal to the distance from the end face of the socket guide pin to the bus bar; the distance from the end face of the plug guide sleeve to the control panel PCB is equal to the distance from the end face of the socket guide sleeve to the bus bar.
3. The aircraft cockpit top control panel in-line box structure of claim 1 wherein the distance from the end face of the guide pin to the control panel PCB is greater than the distances from the end faces of the plug guide pin and the plug guide sleeve, respectively, to the control panel PCB; the distance from the end face of the guide sleeve to the bus bar plate is smaller than the distance from the end faces of the socket guide sleeve and the socket guide pin to the bus bar plate assembly respectively.
4. The aircraft cockpit top control panel in-line box structure of claim 1 wherein the busbar assembly includes a busbar having a front face with a board-to-board connector receptacle, an electrical module with an external shield box, and a guide sleeve assembly, and a back face with a connector mating with an intermediate connector and an electrical module with an external shield box; the electric module is tightly attached to the shielding box through heat conducting glue.
5. The aircraft cockpit top control panel of claim 1 wherein the control panel comprises a PCB board with a board-to-board connector plug and guide pin assembly.
6. The aircraft cockpit top control panel in-line box structure of claim 1 further comprising a spring mechanism in place of the guide pin assembly with a screw assembly, the spring mechanism comprising a spring, a spring mount and a circlip;
the screw assembly comprises a pull-out screw, a fixed washer and a mounting base, and is convenient to take the control panel off the large box body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611132195.0A CN106793651B (en) | 2016-12-09 | 2016-12-09 | Direct-insertion type box structure of control board at top of aircraft cockpit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611132195.0A CN106793651B (en) | 2016-12-09 | 2016-12-09 | Direct-insertion type box structure of control board at top of aircraft cockpit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106793651A CN106793651A (en) | 2017-05-31 |
| CN106793651B true CN106793651B (en) | 2024-05-31 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201611132195.0A Active CN106793651B (en) | 2016-12-09 | 2016-12-09 | Direct-insertion type box structure of control board at top of aircraft cockpit |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| FR3084558B1 (en) * | 2018-07-27 | 2021-02-19 | Safran Electrical & Power | UPPER CONTROL PANEL FOR AIRCRAFT COCKPIT |
| CN113055038B (en) * | 2021-03-08 | 2022-04-05 | 中国电子科技集团公司第三十八研究所 | An airborne high reliability SAM assembly |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5544842A (en) * | 1993-09-21 | 1996-08-13 | Smith; Edward | Apparatus and method for the conversion of a three crew member aircraft cockpit to a two crew member aircraft cockpit |
| CN201550377U (en) * | 2009-10-20 | 2010-08-11 | 大连捷成实业发展有限公司 | Novel case with active plug-in capable of being replaced online |
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| CN205213195U (en) * | 2015-12-03 | 2016-05-04 | 上海航空电器有限公司 | A many panel components mounting structure for aviation cockpit |
| CN206835511U (en) * | 2016-12-09 | 2018-01-02 | 上海航空电器有限公司 | A kind of top control panel for aircraft cockpit direct insertion box body structure |
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| US5544842A (en) * | 1993-09-21 | 1996-08-13 | Smith; Edward | Apparatus and method for the conversion of a three crew member aircraft cockpit to a two crew member aircraft cockpit |
| CN201550377U (en) * | 2009-10-20 | 2010-08-11 | 大连捷成实业发展有限公司 | Novel case with active plug-in capable of being replaced online |
| CN102639358A (en) * | 2009-11-30 | 2012-08-15 | 伊顿公司 | Digital hybrid cockpit control panel system with integrated panel modules and coordinated digital chromaticity control |
| CN102709710A (en) * | 2012-05-18 | 2012-10-03 | 京信通信系统（中国）有限公司 | Active coverage unit and active coverage array formed by same |
| TWM458378U (en) * | 2012-12-28 | 2013-08-01 | Yih Sean Entpr Co Ltd | Thin film panel control device |
| CN203390804U (en) * | 2013-06-25 | 2014-01-15 | 中国商用飞机有限责任公司 | Positioning tooling for installing top control plate of aircraft cockpit |
| CN203630553U (en) * | 2013-12-19 | 2014-06-04 | 集美大学 | Self-assembled modularized household intelligent control panel |
| CN205213195U (en) * | 2015-12-03 | 2016-05-04 | 上海航空电器有限公司 | A many panel components mounting structure for aviation cockpit |
| CN206835511U (en) * | 2016-12-09 | 2018-01-02 | 上海航空电器有限公司 | A kind of top control panel for aircraft cockpit direct insertion box body structure |
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| CN106793651A (en) | 2017-05-31 |
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